System for washing an aero gas turbine engine

ABSTRACT

System for washing a gas turbine engine ( 1 ). The system comprises a spray device ( 33; 90 ) including at least one nozzle ( 54 ) adapted to inject liquid into an inlet ( 110 ) of said engine during a washing operation; a wash unit ( 31, 35 ) adapted to distribute said liquid to said spray device ( 33; 90 ); and a positioning device ( 34 ) adapted to move said spray device in three dimensions, thereby enabling a positioning of said spray device in a washing operation position in said three dimensions relative said engine inlet ( 110 ) without any contact between the spray device ( 33; 90 ) and the engine ( 1 ). The invention further relates to a vehicle for making the inventive system mobile and to a mobile system for serving a gas turbine engine ( 1 ) comprising a mobile vehicle carrying the washing system and a liquid collecting unit ( 116 ) comprising a collecting device ( 114 ) adapted to collect waste wash liquid emanating from the engine during a washing operation of the engine.

This is a nationalization of PCT/EP05/052643 filed Jun. 8, 2005 andpublished in English.

TECHNICAL FIELD

The present invention generally relates to the field of washing gasturbine engines, and more specifically systems and a vehicle for washinga gas turbine engine installed on an aircraft.

BACKGROUND OF THE INVENTION

A gas turbine aircraft engine comprises of a compressor compressingambient air, a combustor burning fuel together with the compressed airand a turbine for powering the compressor. The expanding combustiongases drive the turbine and also result in thrust for propulsion.

Aircraft flying at high altitude ingest the clean air prevailing atthese altitudes. However, at the aerodromes the air contains foreignparticles in form of aerosols which enters the engine with the airstream. Typical particles found in the aerodrome air are pollen,insects, hydrocarbons coming from industrial activities and salt comingfrom nearby sea. While the aircraft is grounded at the airport there areadditional particles to consider such as combustion residues in engineexhaust from taxing aircraft, chemicals coming from aircraft de-icingand ground material such as dust. The majority of the foreign particleswill follow the gas path through the engine and exit with the exhaustgases. However, there are particles with properties of sticking on tocomponents in the engine's gas path, especially in the compressorsection of the engine. This is known as fouling.

Compressor fouling results in a change in the properties of the boundarylayer air stream of the compressor components. The presence of foreignparticles results in an increase of the component surface roughness. Asair flows over the surface the increase of surface roughness results ina thickening of the boundary layer air stream. The thickening of theboundary layer air stream has negative effects on the compressoraerodynamics in form of a reduced mass flow. At the blade trailing edgethe air stream forms a wake. The wake forms a vortex type of turbulencewith a negative impact on the air flow. The thicker the boundary layerthe stronger the turbulence in the wake and the more it reduces the massflow. Further, a thick boundary layer and a stronger trailing edgeturbulence result in a reduced compression gain which in turn results inthe fouled compressor compressing air at a reduced pressure ratio.Anyone skilled in the art of heat engine working cycles understands thata reduced pressure ratio result in a lower thermal efficiency of theengine. The compressor fouling not only reduces the mass flow andpressure gain but also reduces the compressor isentropic efficiency.Reduced compressor efficiency means that the compressor requires morepower for compressing the same amount of air. The power for driving thecompressor is taken from the turbine via the shaft. With the turbinerequiring more power to drive the compressor there will be less power tocreate thrust for propulsion. For the aircraft pilot this means he mustthrottle for more fuel as to compensate for the reduced thrust.Throttling for more fuel means the consumption of fuel increases andthereby increasing the operating costs. The performance loss caused bycompressor fouling also reduces the durability of the engine. As morefuel has to be fired for reaching a required thrust level, follows anincrease in the engine firing temperature. When the pilot on the runwaythrottles for take-off, the engine's hot section components are undercritical high temperature load. Controlling the combustion gastemperature is a key issue in engine performance monitoring. Thecontrolling temperature known as exhaust gas temperature (EGT) ismeasured with sensors in the gas path downstream of the combustoroutlet. The EGT is carefully monitored by logging both temperature andexposure time. During the lifetime of the engine the EGT log isfrequently reviewed. At a certain point it will be required that theengine is taken out of service for an overhaul where hot sectioncomponents are inspected and replaced if required.

Compressor fouling also has a negative effect on the environment. Thedifference in fuel consumption of a virgin engine delivered from thefactory and an engine with a fouled compressor may typically be 1%. Withthe increase of fuel consumption follows an increase of emissions ofgreen house gas such as carbon dioxide. Typically combustion of 1 kg ofaviation fuel results in formation of 3.1 kg carbon dioxide. Further,high combustor temperature has a negative effect to the environment.With the increase of firing temperature follows an increase of NOxformation. NOx formation depends to a large extent on the design of theburner and a general number can not be provided. However, anyincremental temperature rise to a given burner design results in anincrease in NOx formation. Hence, compressor fouling has negativeeffects to aero engine performance such as increasing fuel consumption,reducing engine life and increasing emissions.

A number of engine washing techniques has developed over the years as toreduce or eliminate the negative effects of fouling. The simplestwashing method is taking a garden hose and spraying water into theengine inlet. This method has however limited success due to the simplenature of the process. An alternative method is hand scrubbing theblades with a brush and liquid. This method has limited success as itdoes not enable cleaning of the blades in the interior of thecompressor. Moreover, it is time-consuming. U.S. Pat. No. 5,868,860 toAsplund discloses the use of a manifold for washing of aero engines.Further the patent discloses the use of high liquid pressure as means ofproviding a high liquid velocity, which together with rotation of theengine shaft will enhance the cleaning efficacy. U.S. Pat. No. 6,394,108to Butler discloses a thin flexible hose which one end is inserted fromthe compressor inlet towards the compressor outlet in between thecompressor blades. At the inserted end of the hose there is a nozzle.The hose is slowly retracted out of the compressor while liquid is beingpumped into the hose and sprayed through the nozzle. However, thewashing efficacy is limited by the compressor rotor not being able torotate during washing. Despite existing wash technologies and patentsthere is a need for new technologies enabling practical washing to beconducted in a less labour intensive, low cost, simple and safe way.

SUMMARY OF THE INVENTION

The commercial air traffic has developed into an efficient tool forcarrying passengers and goods from one place to another. The aircraftfleet today comprises of a large number of aircraft types supplied bymany aircraft manufacturers. The engines used for propelling theseaircrafts are manufactured by several engine manufacturers, supplyingengines of different size and with different performancecharacteristics. Engine manufacturers also supply engines that arecompatible with engines from other manufacturers which mean that thereare alternative engines, although not identical, available for the sameaircraft. This result in a large possible combination of aircraftengines on aircraft types. This is found being a disadvantage whenpractising washing as the wash equipment need to be sized and engineeredto meet the individual designs. It is the purpose of this invention tosimplify washing of the engines.

The practising of engine washing described with reference to FIG. 1 isfurther regarded as common knowledge in this field. A cross section viewof a two shaft turbofan engine is shown in FIG. 1. Arrows show the gasflow through the engine. Engine 1 is built around a rotor shaft 14 whichat its front end is connected to fan 15 and at the rear end to turbine16. Turbine 16 drives fan 15. A second shaft 19 is in form of a coaxialto first shaft 14. Shaft 19 is connected at its front end to compressor17 and rear end to turbine 18. Turbine 18 drives compressor 17. Engine 1has an inlet 110 where inlet air enters the engine. Cowling 11 serves asa guide for the inlet air stream. The inlet air flow is driven by fan15. One portion of the inlet air exits at outlet 11. The remainingportion of the inlet air enters into the core engine at inlet 13. Theair to the core engine is then compressed by compressor 17. Thecompressed air together with fuel (not shown) is combusted in combustor101 resulting in pressurized hot combustion gases. The pressurized hotcombustion gases expand towards core engine outlet 12. The expansion ofthe hot combustion gases is done in two stages. In a first stage thecombustion gases expands to an intermediate pressure while drivingturbine 18. In a second stage the hot combustion gases expands towardsambient pressure while driving turbine 16. The combustion gases exitsthe engine at outlet 12 at high velocity providing thrust. The gas fromoutlet 12 together with air from outlet 11 together make up the enginethrust.

A washing device according to prior art consist of a manifold 102 inform of a tube which in one end is connected to a nozzle 103 and theother end connected to a coupling 104. Hose 105 is at one end connectedto coupling 104 while the other end is connected to a liquid pump (notshown). Manifold 102 is resting upon inlet cowling 11 and held in firmposition during washing by securing it with a strap or similar means.The wash procedure begins by cranking the engine shaft with help of theengine's starter motor. The pump pumps a wash liquid to nozzle 103 whereit atomizes and forms a spray 104. The rotation of the shaft results inan air flow through the engine. This air flow will drive liquid throughthe engine and release fouling material. The fouling material isreleased by mechanical and chemical act of the washing liquid. Thecleaning effect is enhanced by the shaft rotation as the wetting ofblades creates a liquid film which will be subject to forces such as theair draught and centrifugal forces during washing.

Prior art describes the use of a manifold with nozzles for injecting thewash fluid into the engine inlet. It is common that the manifold isplaced in the inlet cowling while using the cowling for its support. Themanifold is thus temporarily installed for the washing process and isremoved after completion of the wash. FIG. 2 shows an example of a priorart manifold when installed in a turbofan engine inlet. Similar partsare shown with the same reference numbers as FIG. 1. Manifold 102 isresting on inlet cowling 11 of the air intake to engine 1. Manifold 102is fabricated to fit the shape of the inlet cowling as to be in firmposition during washing. To ensure that the manifold is held in a firmposition, a strap 21 is attached to the manifold outside of the inletand tighten against a hook (not shown) hooked on to the engine outlet.Wash liquid is pumped by a pump (not shown) through hose 105 viacoupling 104 to manifold 102 and further to nozzles 103. Manifold 102 isin form of a tube which serves as a conduit for the wash liquid.Manifold 102 also act as a stiff support to the nozzles as to hold thenozzles in firm position during washing. For a good wash result a properpositioning of the manifold is mandatory. For this purpose the manifoldhas to be designed and engineered with respect to the shape of the inletcowling and the characteristic geometry of the engine. Further, themanifold has to be designed and engineered as to appropriately supportthe nozzles against spray reaction forces during washing.

As mentioned above there are many different aircraft types and manydifferent aircraft engines which result in many different inlet aircowling designs. As the manifold takes support on the inlet cowling thismeans that many different manifolds will have to be manufactured as toservice a large fleet of aircraft. This is a disadvantage as an airlineoperator will have to stock a large number of manifolds.

This invention as described in the preferred embodiments discloses amanifold that has no contact with the inlet cowling. The manifoldaccording to the invention then eliminate the requirement of matchingthe inlet cowling design and thereby the need for a large number ofmanifolds. It is the purpose of this invention to reduce the number ofmanifold the airline operator has to keep in stock.

The manifolds according to prior art are of large dimensions as a resultof the large intake geometry of large aircraft engines. The manifoldsthereby require significant storage space at storage.

The invention as described in the preferred embodiments discloses auniversal manifold that is significantly smaller in size compared toprior art manifolds. It is the purpose of this invention to reduce thestorage space by providing a small manifold.

The manifolds according to prior art design result in significant amountof labour hours to engineer, manufacture and test for fit. Further, themanifold is put in production in only small series as there may not betoo many aircraft with a specific combination of engine and inletcowling. This invention as described in the preferred embodimentsdiscloses a universal manifold applicable to a large range of aircraftand aircraft engines. The manifold according to the invention is inprincipal engineered once and may be put in production in larger series.This will reduce the costs for the universal manifold. It is the purposeof this invention to reduce costs for the airline operator.

Washing aircraft engines may be conducted by the airline operator or bya specialist organisation like an Airport Engine Wash Service Centre.Document EP 628477 describes a device for de-icing for example aircraftscomprising a robot arm having articulated pivotal joints and means forcontrolling the arm in three dimensions and having an effector arrangedwith a number of nozzles for spraying de-icing liquid onto aircrafts.However, the device according to EP 628477 does not have any means for,and is not intended to, wash aircraft engines. If the washing isconducted by a service centre the disadvantage by having many manifoldsin stock is even more an issue of concern as the service centre willservice a large number of different aircraft and aircraft engines. It isthe purpose of this invention to reduce costs for the Airport EngineWash Service Centre operator.

As disclosed in the preferred embodiment of this invention theuniversal, no-contact manifold according to the invention is put andheld in position by the use of an arm such as a robotic arm. The roboticarm is operated from a control panel by an operator adjacent to theengine. The robotic arm allows the universal manifold to be positionedin the intake of the engine without physical contact between theaircraft and the universal manifold. The use of a robotic arm forpositioning the manifold simplifies the set-up operations and makes theset-up safer. The wash operations can be viewed by the operator bydirect eye contact with the engine inlet or by help of a viewing devicesuch as an instant recording camera on the robotic arm. The use of acamera enables the operator to position the manifold and as well viewdetails of the wash operation which he may not otherwise see.

There have been mentioned some issues of concern related to the use ofthe prior art manifold. The use of a robotic arm is a safety devicereducing the risk of accidental damage. The prior art manifold can causedamage to the aircraft, e.g. a dent on the cowling, by accidentalhandling of the manifold during installation or removal. This inventionas described in the preferred embodiments discloses the use of a roboticarm for a simplified and safer positioning of the manifold and therebyreducing the risk of accidental damage. It is the purpose of thisinvention to reduce the risk of accidental damage.

Any work done on the aircraft such as washing the engines requires thatthe operations comply with the instructions given by the AircraftMaintenance Manual. This manual gives instructions on engine washrequirements and limitations such as installing an object like a washmanifold on the engine inlet cowling. By the use of a no-contactmanifold according to the preferred embodiments of this invention it isnot necessary to consult the Aircraft Maintenance Manual for purpose ofinstalling the manifold. It is the purpose of this invention to avoidany conflict with any aircraft operational instructions such as theAircraft Maintenance Manual by a manifold with no contact with theaircraft.

Conducting an engine wash requires that the aircraft has to be taken outof service for some time. It is in the interest of the airline operatorto reduce the time the aircraft is out of service. The use of theuniversal and no-contact manifold according to the invention reduce thetime for the wash operation as the set-up time for the manifold isshortened. Further, the universal and no-contact manifold can beoperated by only one operator present at the aircraft or alternativelyby remote control. It is the purpose of this invention to shorten thetime for the wash operation and to reduce the labour requirement.

Further objects and advantages of the present invention will bediscussed below by means of exemplifying embodiments.

BRIEF DESCRIPTION OF THE DRAWINGS

Preferred embodiments of the invention will now be described in greaterdetail with reference to the accompanying drawings, in which

FIG. 1 shows the cross section of a two shaft turbofan engine withmanifold and nozzles for washing according to prior art.

FIG. 2 shows the manifold installed in the inlet of an aero engineaccording to prior art.

FIG. 3 shows the wash unit with the no-contact spray head according tothe invention.

FIG. 4 a show the application of the invention when washing an ‘underwing’ mounted engine.

FIG. 4 b shows the application of the invention when washing a ‘tail’mounted engine.

FIG. 5 shows spray head details according to the invention.

FIG. 6 shows an alternative embodiment of the spray head.

FIG. 7 a shows washing of the fan of a turbofan engine according to theinvention.

FIG. 7 b shows washing of the core engine of a turbofan engine accordingto the invention.

FIG. 8 shows how the wash procedure is controlled by means of a cameraand distance measuring device installed on the spray head.

FIG. 9 shows the universal, no-contact spray head according to theinvention.

FIG. 10 shows the universal, no-contact spray head and a waste watercollecting device with waste water treatment for reuse of the washliquid.

DESCRIPTION OF PREFERRED EMBODIMENTS

The invention disclosed heir in describes a system including a manifoldthat has no contact with the inlet air cowling. Having no contact withthe inlet air cowling eliminates the issue of manufacturing adaptedmanifolds to the large number of aircraft engine inlet cowlings.Further, the manifold disclosed heir in is universal in the meaning thatit may service small engines as well as large engines as the manifoldhas multi size capabilities. A manifold having multi size capabilityeliminates the issue of manufacturing many manifolds for aircraftengines of varying size.

FIG. 3 shows the application of the universal and non-contact manifoldaccording to the invention. An aero engine 1 installed on an aircraft(not shown) is subject to washing. Wash unit 31 is a unit for deliveringwash liquid to a spray head 33. Spray head 33 includes a manifold 36 fordistributing the liquid to nozzles (not shown for clarity) on manifold36. The nozzles inject the wash liquid into the engine inlet. Thenozzles may either atomize the liquid or inject liquid as a solidstream. Wash unit 31 comprises of the necessary equipment and componentsfor enabling washing such as tanks for storing wash liquid, heaters forheating the liquid, a pump for raising the liquid pressure, controlsrequired to enable and monitor the wash operation. The liquid may bewater only or water with chemicals or chemicals only such as solvents.Typically the liquid is heated as washing with hot liquid as hot liquidenhances the wash result. The wash liquid is pressurized by the pump fordistribution to the nozzles. The controls typically comprise of liquidpressure meter, liquid flow meter, liquid temperature meter and pumpon-off switch. Wash unit 31 may be mobile as to make it practical foruse for washing aircraft engines at an airport. Wash unit 31 may then bepart of a vehicle 32. Vehicle 32 may be a hand towed cart or a motordriven cart or a person carrying vehicle such as a small truck.Alternatively, wash unit 31 may not be mobile.

Spray head 33 is held in fixed position in the inlet of engine 1 byrobotic arm 34. Robotic arm 34 is at one end installed on wash unit 31and has spray head 33 on the other end. Robotic arm 34 has at least onearticulated joint and a wrist enabling appropriate positioning of sprayhead 33 in inlet 301 of engine 1. The robotic arm is moveable with atleast three degrees of freedom. Robot arm 34 operates by a hydraulic orpneumatic or electric or mechanically hand driven operating device (notshown) or may be moved by hand force. In an embodiment of the presentinvention, the robotic arm may comprise one or several telescopic parts.For example, a part between two joints may be telescopic.

Spray head 33 is sized to be smaller than the opening of inlet 301.Spray head 33 is preferably positioned in inlet 301 by operating roboticarm 34 from a control panel (not shown) by an operator. Spray head 33 ispositioned essentially in the centre of the opening of inlet 301. Whenspray head 33 is in its appropriate position there is no contact betweenthe aircraft and the spray head or any other parts of the washingdevice. Wash unit 31 delivers the pressurized wash liquid to spray head33 via conduit 35 where conduit 35 comprises of a flex hose or similardevice for that service. In spray head 33 the liquid is distributed to amultiple of nozzles via manifold 36 where the nozzles have the purposeof injecting the wash liquid into the engine.

FIG. 4 a exemplifies the invention when in position for use when washingan engine of an ‘under wing engine’ type aircraft. Similar parts areshown with the same reference numbers as FIG. 1 and FIG. 3. Aircraft 40has a wing 41 on which engine 1 is installed. Vehicle 32 with the washunit is parked adjacent to the engine. Vehicle 32 is preferably parkedat one side of the engine as not to be standing in the direct air streamduring washing. This is to avoid that any loose objects on the vehiclemay accidentally be brought by the air stream into the engine. Roboticarm 34 holds the spray head with its manifold 36 in position in theengine inlet. There is no contact between the aircraft and the manifoldor any other parts of the wash unit. FIG. 4 b exemplifies the inventionwhen in position for use when washing an engine of a ‘tail engine’ typeaircraft. Similar parts are shown with the same reference numbers asFIG. 1 and FIG. 3. Vehicle 32 with the wash unit is parked adjacent tothe engine. Robotic arm 34 holds the spray head and its manifold 36 inposition in the engine inlet. There is no contact between the aircraftand the manifold or any other parts of the wash unit. The invention isnot limited to the illustrations in FIG. 4 a and FIG. 4 b as there aremany other aircraft of different designs where the invention is equallyapplicable. Further, there may be aircraft where there is an advantageto arrange for the wash equipment to take support by the cowling orother parts of the aircraft.

FIG. 5 shows the details of spray head 33. Spray head 33 is shown in aperspective view where the arrow shows the direction of the engine airflow. Similar parts are shown with the same reference numbers as FIG. 3.Spray head 33 comprises of a unit with essentially rotational symmetrywith axis 501 being the centre of symmetry. When spray head 33 is inposition for washing axis 501 is essentially aligned with the engineshaft centre of symmetry. Spray head 33 has a central body 50. Body 50has a front end 58 faced towards the engine. Body 50 has a rear end 59opposite to front end 58. Rear end 59 is connected to robotic arm 34.Body 50 includes optical sensing device 55 used as an aid forpositioning spray head 33 and for monitoring the wash operation. Opticalsensing device 55 is directed essentially towards the engine inlet.Optical sensing device 55 may comprise of a camera where the camera viewcan instantaneously be viewed by the operator at the control panel.Alternatively, the optical sensing device may comprise of a fibre opticdevice with the same purpose as the camera. Alternatively, there areother means of recoding the view form the spray head. Optical sensingdevice 55 serves the purpose to deliver a view of the engine inlet tothe operator. The camera view is used for helping the operator to alignthe spray head with the engine shaft centre by manoeuvring the roboticarm from the operator's control panel. Further, the camera view enablesthe operator to position the spray head at the appropriate distanceupstream of the engine. Further, the camera view enables the operatormonitor the washing process by delivering a view from the engine centreline during washing. Further, the camera view helps the operator takedecision in adjusting any wash parameter from the view that the cameradelivers. Further, the camera view is a safety improving device as theoperator may stop the wash process as of anything he observes in thecamera.

Body 50 in FIG. 5 include a distance measuring device for measuring thedistance to the engine. Typically the distance measuring devicecomprises of a transmitter 56 and a receiver 57. The distance measuringdevice could comprise of a sound sensing device such as an ultra soundsensing device where the transmitter emits a sound beam which reflect onthe engine nose bullet and where the reflected beam is received by thereceiver. The distance from the transmitter and receiver is thenestimated by the time difference for the signal from the transmitter tothe receiver. Alternatively, the distance measuring device could be anoptical measuring device such as a laser where the transmitter emits alaser beam which reflects on the engine nose bullet and is received bythe receiver. Alternatively, there are other distance measuring devicesthat could be used. The recorded distance is delivered to the operatingpanel where the operator will use the information when adjusting theappropriate position of the spray head upstream of the engine. Duringwashing the measured distance helps the operator control the washprocess by reporting any changes in distances. The distance measurehelps the operator take decision in adjusting any wash parameter if hefinds the distance not to be appropriate. The distance measuring deviceis a safety improving device as the operator may stop the wash processif he finds the distance is not safe. The distance measuring device mayinclude alarms which emit an alarm signal in form of an acoustic soundor a light flash if the distance is out of range. For example, if themeasured distance decreases below a predetermined value. In oneembodiment, this limit value can be adjusted by the operator by means ofthe control panel.

Body 50 include a lamp 52 for illuminating the engine inlet. Theillumination improves the view from the camera as well as the view fromdirect eye contact with the engine inlet. Body 50 may include otherdevice for improving the safety or for improving the wash operation.

As the man skilled within the art easily realizes, can each of thefollowing features: the optical sensing device 55, the distancemeasuring device 56, 57, or the lamp 52 be used independently of theothers. That is, the spray head 33 may, for example, only include theoptical sensing means 55 or only the distance measuring device 56, 57.

Spray head 33 in FIG. 5 shows the manifold as a ring shaped tube, i.e. atorus. Liquid is pumped from the wash unit (not shown) via a hose (notshown) to manifold 36. Manifold 36 is essentially circular with thecircle centre aligned with axis 501. The plane of manifold 36 isessentially perpendicular to axis 501. Manifold 36 is connected to body50. Manifold 36 has multiple nozzles arranged around the manifold fordifferent wash services. For example, Nozzle 53 serves the purpose ofwashing the engine fan. Nozzle 54 serves the purpose of washing the coreengine. Nozzle 510 serves the purpose of washing the nose bullet. Nozzle511 serves the purpose of washing the cowling. In addition to nozzles53, 54, 510 and 511 the manifold may comprise of other nozzles (notshown) for washing other engine details. Manifold 36 has at least onenozzle 54. The nozzles may atomize the liquid into a spray of droplets.Alternatively, the nozzles may deliver the liquid as a non-atomized jet.The objective of using ring shaped manifolds is that the manifolds maybe manufactured from one tube which is bent into a ring requiring onlyone joint (one weld). This is an advantage to alternative designsrequiring many more joints. Any reduction in joints is regarded as asafety feature as joints may brake and can cause damage if loosenedparts enter the engine. Further, the ring shaped manifold is consideredsafe as any accidental contact between the manifold and any aircraftparts would not imply contact with any sharp edges. Alternatively maythe manifold be equipped with a cushion such as rubber foam material(not shown) as to pick up any force in case of an accidental contactwith the engine.

FIG. 6 shows an alternative embodiment of the spray head. Similar partsare shown with the same reference numbers as FIG. 3 and FIG. 5. The ringshaped manifold is here replaced by pipes 61 holding the nozzles inposition. Alternatively, the manifold can be made differently.

FIGS. 7 a, 7 b and 8 shows the application of the invention when washinga turbofan engine. Similar parts are shown with the same referencenumbers as previous figures. FIG. 7 a shows the washing of the fan ofturbofan engine 1 by use of nozzles for washing of the fan. Duringwashing the fan is forced to rotation by the use of the engine startermotor. Nozzle 53 is atomizing the wash liquid into spray 71. The nozzleshave a spray pattern resulting in a distribution of liquid limited onone side by streamline 75 and on the other side by streamline 76. Thespray's distribution at the leading edge of fan blade 72 is essentiallyequal to the total blade length limited by tip point 702 and hub point701. The spray thus covers the whole blade length. Manifold 51 maycomprise of only one nozzle 53 which then only covers a portion of theengine inlet. Wetting of the whole fan is then accomplished by therotation of the fan. FIG. 7 b shows the washing of the core engine ofturbofan engine 1. During washing the engine shaft is rotated by the useof the starter motor. Nozzle 54 is atomizing the wash liquid into spray73. The nozzles have a spray pattern resulting in a distribution ofliquid limited on one side by streamline 77 and the other side bystreamline 78. The purpose of the spray is to deliver liquid into coreengine inlet 74. The core engine inlet is limited by air splitter 705and a point 704 on the hub on the opposite side of air splitter 705. Thespray's distribution at the core engine inlet is equal to the coreengine inlet opening limited by air splitter 705 and point 704. Therebywill the liquid emanating from nozzle 54 enter core engine inlet 74.Further, nozzle 54 is oriented as to enable the liquid to penetrate inbetween the blades during fan rotation. FIG. 7 a and FIG. 7 b describeswashing of the turbofan engine by the use of the engine's starter motor.Alternatively may other starting device be used such as a separate APUstarter. Alternatively, washing may be conducted without rotating theengine shaft.

FIG. 8 shows the use of the camera and the distance measuring device.Similar parts are shown with the same reference numbers as previousfigures. A camera 55 has a viewing angle limited by lines 81. The camerawill provide a view of the engine nose bullet enabling the operator tomove the spray head to the appropriate position for washing. When theengine is cranked by its starter motor the camera view is used formonitoring the shaft rotation. The camera may then be attached to acomputing device (not shown) with software for estimating the rotationalspeed. The rotational speed serves as an input parameter to the operatorwhen to start liquid pumping. Having control of the rotational speed isessential for a good wash result. Further, the camera view allowsviewing of the liquid distribution onto the fan as well as thepenetration of liquid into the core engine.

This view serves as an important input to the operator as he may adjustthe positioning of the spray head or adjust the wash parameters as tobetter serve his objectives. To avoid that the camera lens iscontaminated with air borne liquid, the lens is purged by an air streamsupplied from a compressed air source (not shown). The distancemeasuring device comprise of a transmitter 56 emitting a beam 82 towardsnose bullet 83 where it reflect and returns the reflected beam toreceiver 57. The signal is fed to a computing unit (not shown) forcomputing the distance. The computing unit may be set with alarm levelsas to provide, e.g. an acoustic alarm, if the distance to any objectbecomes critically short. The distance measuring device may de directedtowards other objects than the nose bullet in the engine inlet as toprovide information on measured distances. To avoid that the measuringdevice sensors are contaminated with air born liquid they are purged byan air stream supplied from a compressed air source (not shown).

FIG. 9 shows the universal spray head which will service a large rangeof differently sized engines. Spray head 90 is shown in a perspectiveview where the arrow shows the direction of the air flow. Spray head 90has a central body 91 with similar camera, distance measuring device andlamp as earlier described in spray head 33 in FIG. 5. Spray head 90comprise of multiple ring shaped manifolds 92 each with differentdiameters. Rings 92 are arranged in symmetry around central axis 501.Rings 92 are all essentially in the same plane where the planes areessentially perpendicular to axis 501. The rings are arranged with a gapin between the rings as to allow air flow through the spray head. Eachring comprises of one or multiple nozzles 93 where the nozzle type,number of nozzles and the nozzles spacing is according to the washservice the ring will do. Nozzles may be used for washing of the fan,the core engine, the cowling, the bullet nose or similar service. Inprincipal, the inner rings are used for washing of smaller engines whilethe outer rings are used for washing of larger engines. Further, onering may de dedicated to washing of a specific engine type or a specificfamily of engines. The ring with the largest diameter, i.e. the outerring, has a diameter less than the diameter of the inlet cowling of thesmallest engines that the spray head will service. For example, theengines of the popular passenger carrying commercial airlines have aninlet cowling diameter varying in between 1.5 to 3 meters. The sprayhead to service those engines would then have an outer diameter lessthan 1.5 meter.

For washing of an engine typically only one ring is in service. This isaccomplished by having each ring 92 connected via a conduit to adistributor (not shown for clarity) on the spray head. The distributorcomprise of individual valves for closing each conduit. Prior to set-upfor washing the operator would activate the ring to be in use by openingthe corresponding valve. All other valves would then be closed.

Although spray head 90 is universal in the meaning that it may service awide range of aircraft types and engine types it is practical to havemultiple spray heads that are exchangeable. This may be reasoned bydifferent requirements set by the aircraft's instructions or otherinstructions. Another reason could be a separate spray head for meetingmilitary aircraft requirements. There may be additional reasons. Toaccomplish changing of the spray heads the spray head is mounted on therobotic arm with a coupling enabling an easy exchange.

The invention as here disclosed provides means for reducing the time forwashing as well as reducing labour requirement. FIG. 10 shows thearrangement for engine washing that is both less time consuming and lesslabour intensive compared to prior art. Similar parts are shown with thesame reference numbers as previous figures. The process described heirin would typically require only one operator for conducting the wash. Awash unit 31 supplies wash liquid via conduit 35 to a spray head held byrobotic arm 34. During washing the operator controls the process fromcontrol panel 113. Controlling includes viewing the spray head cameraimage from monitor 112. The waste wash liquid emanating from the engineis collected by collecting device 114 at the rear of the engine. Thecollected waste liquid enters a tank (not shown) in unit 116 via conduit115. Unit 116 may be equipped with wheels for mobility. A suitablecollecting device is described in the international application PCT/SE2004/000922, wherein the content of said application hereby is includedherein by reference. The waste liquid is pumped via conduit 118 to atank in wash unit 31 where the released fouling material is separatedfrom the liquid by an appropriate waste water treatment process. Thetreated water will then be used for washing of next engine or isalternatively dumped into a sewer. While the waste water is beingtreated the operator may move his vehicle 32 and other equipment to thenext engine for set-up for the next wash.

Although specific embodiments have been shown and described herein forpurposes of illustration and exemplification, it is understood by thoseof ordinary skill in the art that the specific embodiments shown anddescribed may be substituted for a wide variety of alternative and/orequivalent implementations without departing from the scope of thepresent invention. This application is intended to cover any adaptationsor variations of the preferred embodiments discussed herein.Consequently, the present invention is defined by the wordings of theappended claims and equivalents thereof.

The invention claimed is:
 1. A washing system for washing a gas turbineengine, said washing system being arranged on a mobile vehicle andcomprising: a spray device including at least one nozzle attached to anozzle carrying body adapted to a streamline inject liquid directly intoan inlet of said engine during a washing operation; a wash unit adaptedto distribute said liquid to said spray device; a positioning deviceadapted to move said spray device in three dimensions, thereby enablinga positioning of said spray device in a washing operation position insaid three dimensions relative said engine inlet without contact betweenthe spray device and the engine during a washing process; a controlpanel adapted to enable an operator to adjust the position of said spraydevice in three dimensions relative said engine inlet by means of saidpositioning device; and a liquid collecting unit separate from the spraydevice and not connected to the engine, comprising a collecting deviceadapted to collect waste wash liquid entrained in an airstream emanatingfrom said engine substantially horizontally during a washing operationof said engine.
 2. The washing system according to claim 1, wherein saidpositioning device comprises a robotic arm including joints enabling amovement of said spray device in said three dimensions.
 3. The washingsystem according to claim 2, wherein said robotic arm includes at leastone telescopic part.
 4. The washing system according to claim 1, whereinsaid spray device further comprises an optical sensing device adapted tomonitor a washing operation of an engine.
 5. The washing systemaccording to claim 4, wherein said optical sensing device is connectedto said control panel and is adapted to deliver a view of said engineinlet to an operator of said washing system at a monitor.
 6. The washingsystem according to claim 4, wherein said optical sensing devicecomprises a camera.
 7. The washing system according to claim 4, whereinsaid optical sensing device comprises a fibre optic device.
 8. Thewashing system according to claim 4, wherein said spray device furthercomprises a distance measuring device adapted to measure a distancebetween said spray device and said engine.
 9. The washing systemaccording to claim 8, wherein said distance measuring device isconnected to said control panel and is adapted to deliver an indicationof the distance between said spray device and said engine, therebyinforming an operator of a present distance between said spray deviceand said engine by means of said monitor.
 10. The washing systemaccording to claim 8, wherein said distance measuring device is an ultrasound sensing device comprising a transmitter adapted to emit a soundbeam and a receiver adapted to receive said beam, wherein said distanceis estimated by the time difference for said beam from said transmitterto said receiver.
 11. The washing system according to claim 8, whereinsaid distance measuring device is optical measuring device comprising atransmitter adapted to emit a laser beam and receiver adapted to receivesaid beam, wherein said distance is estimated by the time difference forsaid beam from said transmitter to said receiver.
 12. The washing systemaccording to claim 7, wherein said distance measuring device furthercomprises an alarm means adapted to emit an alarm signal if saidmeasured distance decreases below a predetermined value.
 13. The washingsystem according to claim 1, wherein said spray device further comprisesillumination means.
 14. The washing system according to claim 1, whereinsaid spray device comprises a substantially ring-shaped manifoldarranged symmetrically about said nozzle carrying body, said at onenozzle being arranged is said manifold.
 15. The washing system accordingto claim 1, wherein said spray device comprises at least one pipearranged at said nozzle carrying body, said at least one pipe beingarranged with at least one nozzle.
 16. The washing system according toclaim 1, wherein said spray device comprises a number of substantiallyconcentric ring-shaped manifolds, each having different diameters andbeing arranged symmetrically about said nozzle carrying body, wherein atleast one nozzle is arranged in each manifold.
 17. The mobile systemaccording to claim 1, wherein said liquid collecting unit is connectableto a tank for storing said waste wash liquid.
 18. The mobile systemaccording to claim 1, wherein said liquid collecting unit is connectableto said wash unit.
 19. The mobile system according to claim 17, whereinsaid tank is connectable to a said wash unit.
 20. The mobile systemaccording to claim 18, wherein said wash unit is adapted to treat saidwaste wash liquid, thereby allowing said treated waste wash liquid to beused in a washing operation.
 21. A liquid wash system comprising: amobile unit; a wash unit associated with the mobile unit for providingwash liquid; one or more nozzles for streamline injecting wash liquidprovided by the wash unit directly into an engine inlet without contactbetween the wash unit and the engine inlet cowling during a washingprocess; and a liquid collector unit separate from the wash unit and notconnected to the engine for collecting used washing liquid that isentrained in an airstream and emanating from the gas turbine engine as aresult of a washing procedure.
 22. The liquid wash system of claim 21,wherein the mobile unit is one of a hand towed cart, a motor drivencart, and a motor vehicle.
 23. The liquid wash system of claim 22,wherein the mobile unit is a motor vehicle, said motor vehicle being asmall passenger truck.
 24. The liquid wash system of claim 21, furthercomprising an articulating arm for use in positioning the one or morenozzles.
 25. The liquid wash system of claim 24, wherein thearticulating arm is operable via one of a hydraulic, pneumatic,electrical, mechanically, hand driven, operating means.
 26. The liquidwash system of claim 21, wherein the wash unit comprises one or moretanks for storing wash liquid.
 27. The liquid wash system of claim 26,wherein the wash unit comprises two or more tanks, at least one forstoring chemical wash solvents, and at least one for storing water only.28. The liquid wash system of claim 26, wherein the wash unit furthercomprising one or more heaters for heating the wash liquid in one ormore of the tanks.
 29. The liquid wash system of claim 28, wherein thewash unit further comprises one or more pumps for raising a pressure inone or more of the tanks, thereby enabling the wash unit to providepressurized washing liquid.
 30. The liquid wash system of claim 29,further comprising one or more controls for use in regulating the washunit, the one or more controls comprising at least one of a liquidpressure meter, a liquid flow meter, a liquid temperature meter, and apump on-off switch.
 31. The liquid wash system of claim 30, wherein oneof the controls further comprises an optical sensing device adapted formonitoring a washing operation.
 32. The liquid wash system of claim 30,wherein one of the controls further comprises a distance measuringdevice for measuring a distance between the one or more nozzles and anengine being washed.
 33. The liquid wash system of claim 30, wherein oneof the controls further regulates one or more heaters for heating thewash liquid.
 34. The liquid wash system of claim 21, wherein the one ormore nozzles comprises a manifold.
 35. A closed loop system for washingengines and collecting and treating waste liquid from the engine washingcomprising: a washing unit for providing a washing liquid into anengine; a collector unit for collecting used washing liquid entrained inan airstream that emanates horizontally from the engine as a result of awashing procedure; a treatment unit for treating the used washing liquidcollected by the collector unit; a transport unit for carrying treatedwashing liquid from the treatment unit to the washing unit to be reusedfor washing engines; and a positioning device adapted to locate saidwashing unit, thereby enabling a positioning of said washing unit in awashing operation position relative to an engine inlet without contactbetween the washing unit and the engine inlet cowling during a washingoperation, wherein the washing unit, the collector unit, the treatmentunit, the transport unit and the positioning device do not come intocontact with the aircraft during a washing operation.
 36. The system ofclaim 35, further comprising one or more mobile units for transportingone or more of the washing unit, collector unit, treatment unit andtransport unit.
 37. A mobile washing system for washing a gas turbineengine of an aircraft having an engine shaft and an inlet cowling, thewashing system comprising: a spray device including a central axis, acentral body, and at least one manifold arranged relative to the centralbody and having at least one nozzle adapted to streamline inject washingliquid directly into an inlet of said gas turbine engine during awashing operation, wherein the spray device is sized to be smaller thanthe opening of the inlet of the gas turbine engine; a wash unit adaptedto distribute said liquid to said spray device; a positioning deviceadapted to locate said spray device, thereby enabling a positioning ofsaid spray device in a washing operation position relative to saidinlet, wherein when the spray device is in the washing operationposition, the central axis is substantially aligned with the engineshaft and there is no contact between the manifold and the inletcowling; and a liquid collector unit for collecting used washing liquidthat is entrained in an airstream and emanating from the gas turbineengine as a result of a washing procedure; and a liquid treatment unitfor treating the used washing liquid providing by the used liquidcollector.
 38. The washing system of claim 37, wherein the liquidtreatment unit comprises at least one of a filter, centrifuge, andseparator for use in treating the used washing liquid.
 39. The washingsystem of claim 37, further comprising a washing unit for providing awashing liquid to the engine.
 40. The washing system of claim 39,wherein the liquid treatment unit is connectable to the washing unit toprovide a closed loop system.
 41. The washing system of claim 40,further comprising one or more mobile vehicles onto which is provided atleast one of the washing unit, the collecting unit or the liquidtreatment unit.